EP1748153B1 - Schaufel einer Strömungsmaschine und Strömungsmaschine mit einer solchen Schaufel - Google Patents

Schaufel einer Strömungsmaschine und Strömungsmaschine mit einer solchen Schaufel Download PDF

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Publication number
EP1748153B1
EP1748153B1 EP06116912.4A EP06116912A EP1748153B1 EP 1748153 B1 EP1748153 B1 EP 1748153B1 EP 06116912 A EP06116912 A EP 06116912A EP 1748153 B1 EP1748153 B1 EP 1748153B1
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EP
European Patent Office
Prior art keywords
blade
segment
fraction
along
connection
Prior art date
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Active
Application number
EP06116912.4A
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English (en)
French (fr)
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EP1748153A1 (de
Inventor
Jacques Boury
Erwan Botrel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
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SNECMA SAS
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a turbomachine blade having a free end comprising an end wall on which a rim protrudes.
  • This may be, for example, a turbine rotor blade or a turbojet compressor.
  • FIGS. 1 and 2 represent the free end of a turbine rotor blade 1 of known type.
  • This blade has at its free end 3 an open cavity, or bath 2, delimited by an end wall 8 and a flange 9, of closed contour, projecting from the periphery of this wall.
  • This rim runs along the extrados side 4, the leading edge 6, the intrados side 5 and the trailing edge 7 of the blade.
  • the documents US 2004/197190 A1 , EP-A-1231359 , US Patent 5261789 and GB 2155558A disclose blades of this type.
  • the vanes 1 of the rotor When they are mounted inside a turbojet, the vanes 1 of the rotor are surrounded by a ring 30, shown in FIG. figure 2 .
  • the rim 9 makes it possible to protect the end wall 8 from friction with the ring 30.
  • it makes it possible to optimize the clearance J between the free end 3 of the blade and the ring 30 so as to limit the passage of gas at this level.
  • the aerodynamic design of a turbine blade means that the distance from the leading edge to the trailing edge of the blade is greater on the extrados side than on the underside side.
  • This pressure gradient is also at the origin of the passage of a certain volume of gas F, in the clearance J, between the flange 9 and the ring 30, these gases F moving from the intrados to the extrados .
  • this phenomenon is detrimental to the efficiency of the turbine because the F gases do not work to rotate the rotor.
  • the present invention aims to limit the volume of gas F passing from the lower surface to the upper surface between the flange and the ring, in order to improve the efficiency of the turbomachine.
  • the invention relates to a turbomachine blade according to claim 1.
  • the invention aims to increase the distance traveled by the gas flowing on the underside side along said flange. These gases are hereinafter called intrados gas.
  • the intrados gases flow along the portion of said second portion between the leading edge and the connection zone, and along said first portion.
  • the distance they travel on the intrados side is therefore greater than the one they traveled with a dawn of the type of Figures 1 and 2 .
  • the flow rate of these gases is higher and the static pressure they exert on the flange, on the underside side, is lower.
  • the static pressure exerted by the extrados gases is the same as with a dawn of the type of Figures 1 and 2 because the distance that these gases run along the rim, on the extrados side, remains the same.
  • Examples of dawn 11 shown on the Figures 3 to 5 are turbo-reactor high pressure turbine rotor blades. Every dawn 11 has a foot 12 and a free end 13 opposite the foot 12. The blade 11 is hollow so that it can be cooled from the inside by fresh air. When mounted inside a turbojet engine, the blade 11 is surrounded by a ring 30, shown in FIG. figure 4 .
  • the blade 11 has an aerodynamic profile: it has a rounded upstream edge, or leading edge 16, and it tapers to its downstream edge, or trailing edge 17. It also has two opposite sides: one side convex extrados 14 and a concave intrados 15 side.
  • the free end 13 of the blade comprises an end wall 18 extending over the entire end thereof and on which protrudes a flange 19.
  • This flange is formed of two portions 20 and 21.
  • connection zone 22 is a zone of the flange 19 situated at the periphery of the end wall 18. on the suction side of the blade, between the leading edge 16 and the trailing edge 17.
  • the connection zone 22 is located at a significant distance from the trailing edge 17.
  • the second portion 21 of the flange 19 is formed solely of the three segments 21a, 21b and 21c so that the connecting segment 21c extends the driving segment 21b.
  • the second portion 21 of the flange comprises a fourth segment, said intrados segment 21d, which runs along a portion of the intrados side of the blade 15.
  • This segment of intrados 21d extends the driving segment 21b and is it even extended by the connecting segment 21c.
  • the first portion 20 of the flange 19, the extrados segment 21a, the driving segment 21b and the optional segment of the underside 21d all run along the periphery of the end wall 18 of the blade.
  • This periphery being generally curved, these flange portions 19 are also curved.
  • the connecting segment 21c is also curved.
  • the second portion 21 of the flange 19 has a closed contour which defines with the end wall 18 a bath 24 of limited size relative to baths known hitherto.
  • the invention makes it possible to increase the speed of the intrados gases along the rim 19 by increasing their travel distance.
  • the intrados gases circulate on a portion of the driving segment 21b, on the possible lower section 21d, on the connecting segment 21c, then on the first portion 20 of the flange 19, before reaching the edge of flight 17.
  • the length of the first portion 20 of the rim 19 is increased.
  • the distance separating the connecting zone 22 from the leading edge 16, measured along the side 14, is less than the distance separating the zone 22 from the trailing edge 17, also measured along the extrados side 14.
  • the connecting segment 21c plays an important role since it guides the gases towards the first portion 20 of the flange 19.
  • junction zone between the connecting segment 21c and the first portion 20 of the flange is curved in order to avoid creating turbulence in the flow of the intrados gases at this level.
  • This junction zone corresponds to the part of the connection zone 22 turned towards the intrados side 15.
  • the connecting segment 21c and the first portion 20 of the Rim 19 together form a convex curve towards the upper surface of the blade.
  • the closed contour of the bath 24, materialized by the second portion 21 of the flange 19, has the general shape of a meniscus having its first rounded end, along the leading edge 16 of the blade, and its second end at level of the connection area 22.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (9)

  1. Schaufel einer Turbomaschine, die ein freies Ende (13) mit einer endseitigen Wand (18), an der ein Rand (19) vorspringt, aufweist, wobei dieser Rand umfaßt:
    einen ersten Abschnitt (20), der von der Austrittskante (17) der Schaufel ausgeht und an der Rückseite (14) der Schaufel bis zu einem Verbindungsbereich (22) entlangläuft, sowie einen zweiten Abschnitt (21) mit geschlossener Kontur, der im Bereich des Verbindungsbereiches (22) mit dem ersten Abschnitt (20) verbunden ist, wobei dieser zweite Abschnitt (21) an der Rückseite (14) der Schaufel entlanglaufend den ersten Abschnitt (20) verlängert, an der Eintrittskante (16) der Schaufel entlangläuft und sich an den Verbindungsbereich (22) anschließt,
    wobei der zweite Randabschnitt (21) ein Rückseitensegment (21 a), welches an der Rückseite der Schaufeln entlangläuft, ein Eintrittssegment (21 b), welches an der Eintrittskante (16) der Schaufel entlangläuft, sowie ein Verbindungssegment (21 c), das sich von der Eintrittskante (16) oder der Vorderseite (15) der Schaufel bis zu dem auf der Rückseite (14) der Schaufel gelegenen Verbindungsbereich (22) erstreckt, umfaßt,
    wobei die endseitige Wand (18), der erste Abschnitt (20) und das Verbindungssegment (21 c) einen auf der Vorderseite der Schaufel seitlich offenen Hohlraum begrenzen, so daß die auf der Vorderseite zirkulierenden Gase entlang dem Verbindungssegment (21 c), entlang dem Verbindungsbereich (22) und entlang dem ersten Abschnitt (20) strömen,
    wobei diese Schaufel dadurch gekennzeichnet ist, daß der entlang der Rückseite (14) gemessene Abstand zwischen dem Verbindungsbereich (22) und der Eintrittskante (16) kleiner ist als der entlang der Rückseite (14) gemessene Abstand zwischen dem Verbindungsbereich (22) und der Austrittskante (17).
  2. Schaufel nach Anspruch 1, dadurch gekennzeichnet, daß der zweite Randabschnitt (21) ferner zwischen dem Eintrittssegment (21 b) und dem Verbindungssegment (21 c) ein Vorderseitensegment (21 d) umfaßt, das an einem Teil der Vorderseite (15) der Schaufel entlangläuft.
  3. Schaufel nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß der erste Abschnitt (20), das Rückseitensegment (21 a), das Eintrittssegment (21 b) und das mögliche Vorderseitensegment (21 d) an dem Umfang der endseitigen Wand (18) der Schaufel entlanglaufen.
  4. Schaufel nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß das Verbindungssegment (21 c) gebogen ist.
  5. Schaufel nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß der Verbindungsbereich zwischen dem Verbindungssegment (21 c) und dem ersten Abschnitt (20) des Randes (19) gebogen ist.
  6. Schaufel nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß das Verbindungssegment (21 c) und der erste Abschnitt (20) des Randes zusammen eine in Richtung der Rückseite (14) der Schaufel konvexe Krümmung bilden.
  7. Schaufel einer Turbine eines Turbostrahltriebwerks, nach einem der vorhergehenden Ansprüche.
  8. Turbine, die eine Schaufel nach einem der Ansprüche 1 bis 7 umfaßt.
  9. Turbomaschine, die eine Schaufel nach einem der Ansprüche 1 bis 7 umfaßt.
EP06116912.4A 2005-07-26 2006-07-10 Schaufel einer Strömungsmaschine und Strömungsmaschine mit einer solchen Schaufel Active EP1748153B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0507925A FR2889243B1 (fr) 2005-07-26 2005-07-26 Aube de turbomachine

Publications (2)

Publication Number Publication Date
EP1748153A1 EP1748153A1 (de) 2007-01-31
EP1748153B1 true EP1748153B1 (de) 2013-09-18

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Country Link
US (1) US7661926B2 (de)
EP (1) EP1748153B1 (de)
FR (1) FR2889243B1 (de)
RU (1) RU2403403C2 (de)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8500396B2 (en) 2006-08-21 2013-08-06 General Electric Company Cascade tip baffle airfoil
US7686578B2 (en) * 2006-08-21 2010-03-30 General Electric Company Conformal tip baffle airfoil
US7607893B2 (en) * 2006-08-21 2009-10-27 General Electric Company Counter tip baffle airfoil
EP2397653A1 (de) * 2010-06-17 2011-12-21 Siemens Aktiengesellschaft Plattformsegment zur Stützung einer Gasturbinenleitschaufel und Kühlungsverfahren
EP2530330B1 (de) * 2011-06-01 2016-05-25 MTU Aero Engines AG Laufschaufel für einen Verdichter einer Turbomaschine, Verdichter sowie Turbomaschine
US20150300180A1 (en) * 2014-04-22 2015-10-22 United Technologies Corporation Gas turbine engine turbine blade tip with coated recess
FR3023635B1 (fr) 2014-07-10 2018-05-25 Safran Aircraft Engines Procede de modelisation d'une baignoire d'une aube
FR3027951B1 (fr) * 2014-11-04 2019-12-13 Safran Aircraft Engines Baignoire de sommet d'aubes d'une turbine de turbomachine
US20160258302A1 (en) * 2015-03-05 2016-09-08 General Electric Company Airfoil and method for managing pressure at tip of airfoil
US10107108B2 (en) 2015-04-29 2018-10-23 General Electric Company Rotor blade having a flared tip

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2155558A (en) * 1984-03-10 1985-09-25 Rolls Royce Turbomachinery rotor blades

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5261789A (en) * 1992-08-25 1993-11-16 General Electric Company Tip cooled blade
US6382913B1 (en) * 2001-02-09 2002-05-07 General Electric Company Method and apparatus for reducing turbine blade tip region temperatures
US6652235B1 (en) * 2002-05-31 2003-11-25 General Electric Company Method and apparatus for reducing turbine blade tip region temperatures
US6991430B2 (en) * 2003-04-07 2006-01-31 General Electric Company Turbine blade with recessed squealer tip and shelf

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2155558A (en) * 1984-03-10 1985-09-25 Rolls Royce Turbomachinery rotor blades

Also Published As

Publication number Publication date
US7661926B2 (en) 2010-02-16
FR2889243A1 (fr) 2007-02-02
US20070025857A1 (en) 2007-02-01
RU2006127074A (ru) 2008-01-27
FR2889243B1 (fr) 2007-11-02
RU2403403C2 (ru) 2010-11-10
EP1748153A1 (de) 2007-01-31

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